Method for launching naval mines

ABSTRACT

An air-based vertical launch system is described by means of which ballistic missile defense can be achieved effectively from a large aircraft. A method for ensuring safe missile egress is proposed. A method for ensuring that the missile strikes the ballistic missile payload section is also proposed. Together, the air basing method employing vertical (or near-vertical) launch and semi-active laser guidance yield an affordable and operationally effective missile defense against both tactical and long-range ballistic missiles. The affordability of missile defense is enhanced by the ability of an aircraft equipped with a vertical launcher to simultaneously carry out several defensive and offensive missions and to provide other capabilities such as satellite launch at other times. Methods for employing an aircraft equipped with a vertical (or near-vertical launcher) and one or more of the proposed egress assurance mechanisms in offensive ground attack missions, mine laying, and satellite launch missions are also proposed.

CROSS REFERENCE TO RELATED APPLICATIONS

This application claims rights under 35 USC119 (e) from U.S. patentapplication Ser. No. 60/468,850, filed May 6, 2003, the contents ofwhich are incorporated herein by reference.

BACKGROUND OF THE INVENTION

1. Field of the Invention

The present invention relates to methods and apparatus for launchingmissiles and more particularly to airborne methods and apparatus forlaunching missiles.

2. Brief Description of Prior Developments

Surface-based ballistic missile defense concepts for boost or ascentphase intercepts have limitations that severely limit operationalutility and impact total system cost. Operational limitations stem fromtransportation difficulties and politically-derived basing constraints.These in part stem from surface-launched missile design imperatives thatforce designs to be very large. Methods for employing smaller missilesrequire numerous launch platforms to meet military requirements and thushave high system deployment and operational costs. Air launch couldreduce some of these inhibitors, but conventional air launch modespreclude full exploitation of the potential advantages of air basing.Observation of the inherent difficulties of alternative surface,subsurface, space and air launch modes led to the inventor'sconsideration of the known benefits of vertical launch as employed innaval ships. Several difficulties for air-based vertical launch thatprecluded serious consideration in the past are solved by thisinvention. Given a means to solve air-based vertical launch egressproblems, expected benefits appeared achievable and unexpected benefitsemerged.

SUMMARY OF INVENTION

The present invention is a method for providing a defense againstballistic missiles. An intercepting missile is first vertically mountedin an aircraft. The ballistic missile is then acquired and tracked. Thevertically-mounted intercepting missile is then safely launched throughapplication of one or more air based vertical launch egress assurancemechanisms. The intercepting missile achieves very high velocity byvirtue of the high altitude launch and efficient vertical launchtrajectory that together maximize the amount of propulsive energyavailable to accelerate the intercepting missile to a speed adequate tocatch the boosting threat. The aircraft then directs the interceptingmissile to a position where it can detect, home on, and subsequentlyimpact against the ballistic missile. The aircraft uses large optics totrack the ballistic missile and designates the payload of the ballisticmissile with a laser. The intercepting missile detects the laserillumination with a semi-active laser (SAL) seeker allowing missile toimpact on the ballistic missile warhead and destroying the payload.

The present invention employs a vertical or near-vertical launcher toachieve the interceptor performance required to achieve the short timeof flight required for success in the ballistic missile defense mission.The invention provides egress assurance mechanisms that provide themissile defense benefit. The invention will also enable a number ofadditional missions to be executed more effectively or more efficientlyby virtue of the increased magazine capacity, mission flexibility andmissile kinematic efficiencies of a high altitude aircraft employing avertical or “near” vertical launcher. The present invention providesegress assurance mechanisms that taken together extend the state of theart to make a vertical launcher practical for aircraft and thus enablesthese applications to be developed with their attendant efficiencies andcost savings both in individual missile costs and in force structure(number of airplanes) required to accomplish a given mission. Examplemissions that would benefit from this invention include test targetlaunch, unmanned air vehicle launch, cruise missile launch, air defensemissile launch air space denial missions, and others.

The present invention also encompasses a method for launching offensiveballistic and aeroballistic missiles. An offensive missile is firstvertically mounted in an aircraft. An emerging target is then detected,identified, and its position determined in Global Positioning System(GPS) coordinates. The vertically-mounted offensive missile is thensafely launched through application of one or more egress assurancemechanisms. The offensive missile then flies to the position directed bythe aircraft where it releases a precision guided munition (PGM) payloadto thereby accomplish a time-critical strike with a reduced number oflaunching platforms.

The present invention also encompasses a method for launching smallsatellites into earth orbit. A satellite launch vehicle is first mountedvertically (or at a forward lean angle to accommodate a longer missile)in an aircraft. The aircraft flies to a preferred launch position toyield a desired orbital inclination. The vertically-mounted launchvehicle is then safely launched through application of one or moreegress assurance mechanisms. The launch vehicle then executes ascent toan appropriate orbital insertion maneuver and releases the smallsatellite payload to thereby accomplish a low cost satellite launch. Theaircraft can carry a number of launch vehicles and subsequently launcheach over a period of time depending on aircraft endurance and therebyinsert a small constellation of small satellites for space science,commercial, or space superiority missions.

The present invention also encompasses a method for launching andinserting naval or other mines into a preplanned pattern from greatdistance using ballistic and aero ballistic missiles. A missileincorporating a mine payload is first vertically mounted in an aircraft.The minefield position is determined in Global Positioning System (GPS)coordinates. The vertically-mounted mine payload missile is then safelylaunched through application of one or more egress assurance mechanisms.The mine payload missile then flies to the position directed by theaircraft where it releases the mine payload to thereby deploy aminefield without exposing the launch aircraft to hostile defenses.

A method for launching UAVs from great standoff comprising the steps ofplacing the UAV in a missile bus consisting of a dual-thrust boosterwith TVC, a GPS-aided INS, a retarding device, a separating shroud, anda UAV initialization device, vertically mounting the missile bus in anaircraft, launching the UAV bus to release the UAV at a prescribedlocation based on GPS coordinates.

A method for launching a missile having a motor from a launch tubecomprising the steps of positioning a self-erecting launch rail slide inthe cavity on one side of the launch tube so as to index the missile onloading; igniting the missile motor so that the rail is pulled upwardlyby the missile during egress from the launch tube until the rail isstopped by a mechanical limit that also unlatches the rail from shoesattached to the missile and forcing the shoes along the remaining lengthof the rail until the motor clears the aircraft, whereby lateral tippingmotions are prevented.

A method for launching a missile having a motor from a launch tubecomprising the steps of positioning rocket nozzles upwind of each launchtube; expelling high-velocity gases from a rocket motor, the missilemotor, or some other gas generator through the nozzles adjacent to thelaunch tube; deflecting the ambient airflow around the missile using thegas flow so created until the missile has egressed from the launch tube;reducing thereby the drag loads on the missile and the resultant tippingforces.

A method for launching a missile having a motor from a launch tubecomprising the steps of positioning an erectable deflector upwind ofeach launch tube; extending the deflector during the launch sequenceusing motors or hydraulic actuators; deflecting the ambient airflowaround the missile using the deflector until the missile has egressedfrom the launch tube; extending the height protected through the use ofhigh-velocity gas jets mounted in the top of the deflector; withdrawingthe deflector back into the launcher; reducing thereby the drag loads onthe missile and the resultant tipping forces.

BRIEF DESCRIPTION OF THE DRAWINGS

The present invention is further described with reference to theaccompanying drawings, wherein:

FIG. 1 is a schematic drawing illustrating a preferred embodiment of theoperation of the air-based vertical launch ballistic missile defensemethod of the present invention;

FIG. 2 is a schematic drawing illustrating a preferred embodiment ofgeneral launcher design features for an air-based vertical launchballistic missile defense method of the present invention;

FIGS. 3 a-3 e are schematic drawings illustrating self-erecting guiderails for launch egress attitude control used in a preferred embodimentof the air-based vertical launch method of the present invention;

FIGS. 4 a-4 g are schematic drawings illustrating fixed tube launcherdetails used in a preferred embodiment of the air-based vertical launchmethod of the present invention;

FIG. 5 is a schematic drawing illustrating an air-based verticallauncher general aircraft configuration (Boeing 747-400 ER) used in apreferred embodiment of the air-based vertical launch missile defensemethod of the present invention;

FIG. 6 is a schematic drawing illustrating a preferred embodiment of thegeneral sequence of operations of the air-based vertical launcher methodof the present invention;

FIGS. 7 a and 7 b are schematic drawings illustrating a time-criticalstrike in a preferred embodiment of air-based vertical launch methodlaunching offensive missiles of the present invention;

FIG. 8 is a schematic drawing of an alternative modular embodiment ofthe air-based vertical launch method of the present invention;

FIGS. 9 a through 9 g are schematic drawings of alternative embodimentsof apparatus for launch egress attitude control (egress assurancemechanisms) used in alternative embodiments for the air-based verticallaunch method of the present invention;

FIG. 10 is a schematic drawing of alternative embodiments of apparatusfor powering missile launch used in the preferred and in alternativeembodiments for the air-based vertical launch method of the presentinvention;

FIG. 11 is a schematic drawing of alternative embodiments of tiltedlauncher apparatus for reducing missile egress loads used in thepreferred and in alternative embodiments for the air-based verticallaunch method of the present invention; and

FIG. 12 is a schematic drawing of alternative embodiments of aircraftapparatus for reducing missile egress loads used in alternativeembodiments for the air-based vertical launch method of the presentinvention.

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENT

Referring to FIG. 1, the method of the present invention maybe carriedout with a jumbo aircraft 10 with air refueling capability. Thisaircraft is equipped with a laser trader designator 12, an IRST 14 and alaser ranger 16. The aircraft is also equipped with BMC2 andcommunications; a vertical or near vertical launcher 22, and a ballasttransfer system 24. The ballast transfer system includes a tank and pumpassembly 26, a aft tank and pump assembly 28, and an intermediateconduit tube between the two tanks. There is also an automatic transientload compensation flight control adjoint 32, an interceptor containing akill vehicle with a SAL seeker 34, and an interceptor link 39.

Aircraft deploy to theater based on 24 hour warning, establish 1-2patrols using 3-4 aircraft each. Theater assets detect a threat, andprovide a cue via existing and planned BMC2 and communications networks.IRST detects the threat once it rises above clouds or horizon. Once TBMis in track, IRST cues Laser Ranger which acquires and tracks thethreat. The aircraft BMC2 Node cues other BMC2 Nodes. IRST, Optics, andLaser Ranger track threat and provide a precision 3-D track (BMC2 passestrack to other users through BMC2 network). Node makes engage decision(or accepts engage order), then initializes and tests interceptor toassure it is safe for launch. Interceptor is launched using safe egressapparatus. Ballast transfer system compensates for e.g. shift. Flightcontrol compensates for egress transients. Link antenna acquires andtracks interceptor beacon, establishes interceptor Link, receivestactical TLM. Weapon control updates and uplinks predicted interceptpoint. Laser Designator Optics allow aim point selection and 3-D track(with Laser ranger). Laser designator illuminates desired hit point oncold body. SAL Seeker detects Laser energy and homes to hit point (evenafter staging event). IRST provides mission assessment data, cue datafor subsequent defense layers

FIG. 1 is the general concept of operations for the Air-Based VerticalLaunch (ABVL) Ballistic Missile Defense (BMD) concept. The aircraft canutilize launch cues from external sensors to cue onboard sensors or canemploy its own surveillance sensors to detect ascending ballisticmissiles. The aircraft then employs its laser ranger to acquire andtrack the ballistic missile and to develop a high-fidelitythree-dimensional (3D) track. The aircraft has a battle managementcommand and control (BMC²) system and organization that can receiveengagement orders from external BMC² or initiate engagement underdoctrinal control from BMC² based on external or onboard sensor data.The aircraft can provide its 3D track information to the external BMC²and other engagement assets through the common BMC² communications. Theaircraft develops a predicted intercept point and upon refining theprediction uncertainty to within the missiles divert range, initializesand launches a missile. The aircraft missile link system acquires themissile and provides up and down communication with the missile. Theaircraft continues to track the ballistic missile with a high-fidelity3D track, providing updates to improve probability of intercept asadditional data improves the solution. Before the kill vehicle (KV)seeker initiates search, the aircraft acquires the threat missile usingthe large aperture laser director optics, selects the aim point, andilluminates the threat with its designation laser. The missile seekeracquires the reflected laser energy and homes to impact on the laserspot centroid. The kinetic energy of the KV at the combined strikevelocity destroys the payload. The intercept is observed by the laserdesignator optics and a Battle Damage Assessment (BDA) report is passedon to subsequent defense layers for further action if required.

FIG. 2 is an illustration of the vertical launcher in the ABVL BMDapplication. Referring to FIG. 2, the vertical launcher includes upperdoors 62, an ablative upper tube extension 64, an upper aircraft skin 66with stiffening ablative point, and a plurality of steel launch tubes68. The missile 70 in a canister fits in the launch tubes. The canisteregress rail 72 also fits the launch tube slot. Steel launcher walls 74provide protection and distribute loads. There is also a lower aircraftskin 76 with ablative stiffening point. The launcher also includes alower sill 78 with latches, an ablative lower tube extension 80, lowerdoors 82, and a load distribution structure 84.

The launcher is located aft of the wing carry-through structure and iscentered on the aircraft centerline. There is a bottom sill for eachcanister and this sill includes a restraint that prevents canistermotion during aircraft operation, absorbing shock and mitigatingvibrations transmitted to the missile. Below each launch tube andcanister are two doors opening at the center towards the sides of theaircraft. These doors are quickly opened during missile initialization.The upper doors operate similarly. Failure of any door to openinterrupts the launch sequencer, which then selects and initializesanother missile. The aircraft skin around the launcher section isstiffened and painted with ablative paints to protect the skin frompressure and thermal loads due to motor ignition and subsequent plumeimpingement. In this illustration, 18 large missiles (32″ diameter) arecontained in a vertical launcher section with 6 rows of 3 missiles each.Smaller missiles would allow a significant increase in loadout capacity.The launcher section has protection from shrapnel on all 6 sides. Thelaunch tubes provide additional protection, as do the canistersthemselves. The launcher section also provides thermal protection to themissiles within and provides some protection to the aircraft to providetime for aircrew escape in the event of accidents.

Referring to FIGS. 3 a-5 d, the air based vertical launch canister andrail assembly includes a booster case 86, an upper shoe 88, a canister90, a rail tank 92, and a rail 94. There is also a slide assembly 96, adetent 98, a motor 100, a Teflon bearing 102; and a mount bracket 104.There is also a slide assembly which includes a rail track 106, a rail108 and wheels 110. The rail track includes an upper track 112 and alower track 114. There is also a lower shoe 116. The apparatus alsoincludes a launch tube 118, canister rings 120, a deflector 124 and aspace 126. The missile 128 is housed within the canister.

FIGS. 3 a-3 e illustrate the use of a self-erecting guide rail employedto facilitate missile egress. The guide rail itself has a narrow slot atthe lower section and a wide slot in the upper section. The missile hastwo launch shoes: a narrow one at the aft end of the booster and a wideshoe at the upper end. The spacing between shoes defines the distancebetween the wide and narrow slots such that the lower shoe is releasedfrom the narrow slot at the same instant as the wide shoe is releasedfrom the upper slot. This scheme is used in several naval guided missilelaunchers. The guide rail itself is mounted inside a slot within whichit can easily slide. This apparatus is similar in function to a commondrawer slide and is capable of handling the missile mass and egressloads (perhaps with wheeled runners). The guide rail is constrained bywedge-shaped nylon pads on either side of the aft launch shoe. When themotor ignites, the rail moves forward with the launch shoe until therail reaches a stop mechanism near the top of the canister trough. Thestop mechanism dampens the impact shock and prevents further upwardmotion of the rail. At the stop mechanism location the slot is slightlywider, allowing the nylon wedges to spread outward. The aft shoe canthen be pressed past the wedges to ride freely up the remaining railsection to the release point. Upon reaching the release point, airflowmoving aft over the aircraft pulls the missile free of the rail at bothends simultaneously, minimizing the tip-off that would otherwise beencountered at egress. The rail itself is then retracted back into thecanister by a spring that attaches the rail to its original position andthat was extended by force from the motor thrust during extension of therail. A stopper dampens the impact of the rail as it returns to thebottom of the track and captures the rail to prevent rebound. This samelatch is used to prevent missile motion in the canister at times otherthan launch and is mechanically released during the launch sequenceprior to motor ignition. If release doesn't occur, the motor ignition isprevented by the launch sequencer, which then selects and initializesanother missile. A vertical launcher is to be fitted into an existingaircraft to provide for efficient launch of missiles intended tointercept ballistic missiles. FIGS. 4 a-4 g illustrate details of apreferred embodiment of an ABVL using fixed array of launch tubes. Thevertical launcher consists of hollow steel (or other suitable material)tubes that serve to direct the rocket motor exhaust products out throughdoors on the bottom of the fuselage and directs the missile throughdoors fitted on the top of the fuselage. Each missile is fitted in alauncher tube. A collection of tubes (array) may be located closetogether as near the aircraft c.g. as possible given existing aircraftstructures and equipment (as illustrated in FIG. 5 for a Boeing 747-400ER aircraft). The vertical launcher tubes and doors minimize theignition shock and mass flow effects on the aircraft. The aircraftstructure in the vicinity of the vertical launcher will be stiffened andcoated to deal with pressure and thermal effects due to motor plumeimpingement upon egress. The collection of tubes comprising the launcherwill be enclosed in steel (or other material) bulkheads to provideprotection to the missiles from external hazards and to isolate thelauncher from surrounding aircraft spaces.

FIG. 6 illustrates the general sequence of operations for an aircraftequipped with a vertical launcher in the preferred embodiment. Referringto FIG. 6, an aircraft is deployed to be theater based on 24 hr warning,establishing 1-2 patrols using 3-4 aircraft each. An Aircraft BattleManagement Command and Control establishes communications with forceBMC2. The BMC2 makes engage decision, issues launch order. Weaponcontrol determines launch safety and hazard areas for booster impact andfailure mode trajectories. Missile selected, initialized, pre-launchoperability tested (new missile selected if test fails). The launcherdoors open and dual thrust booster ignited. Egress assurance mechanismsoperate to ensure missile and aircraft safe operation. The ballasttransfer system rapidly pumps water from forward tank to aft tank tocompensate for c.g. shift (returned later in consort with a/c fueltransfers). Adjunct aircraft flight control anticipates, compensates foregress transients (plume impingement, airflow disruption, c.g. motion)and missile stabilizers deploy (if used). Missile TVC provides safeegress to planned thrust ramp-up condition at position 13 w. Missilebooster ramps up to full thrust. At position 134 a link antenna acquiresand tracks the missile beacon, establishes a missile link, and receivestactical TLM. The weapon control updates and uplinks predicted interceptor payload release point. A missile flies to payload release window 136using GPS aided INS guidance, linked updates, and TVC or aerocontrol andthe payload completes its mission a position 138. A launch controllerwill communicate with all missiles to monitor health and to initiate andlaunch missiles under the direction of a weapon control system. A pairof water tanks and a pump is employed to rapidly counteract the effectof missile launch on the aircraft c.g. The launch controllerautomatically pumps water from a tank ahead of the c.g. to a tank faraft in the aircraft during launch. This flow can be used in combinationwith the existing aircraft fuel redistribution system to maintaindesired c.g. limits for stability and control. In addition, thetransient loads on the aircraft due to the launch event will bepredicted based on measurement of the flight conditions at launch andwill be automatically compensated for by an automated flight controlsystem adjunct to the existing flight control system. The transientloads include ignition shocks, pressure loads, plume impingement loads,and airflow-disruption-derived lift and drag changes. These transientswill be predictable based on missile motor characteristics and aircraftflight conditions. Aircraft inertia characteristics are expected tomitigate response to these transient loads but automated response ispreferred to manual pilot compensation. The automated system can alsocompensate for loads induced under a low probability adverse event, suchas a restrained firing, in which the missile might not release from therail. Those skilled in the art will, however, appreciate that, as aworst-case design consideration, both aircraft control and launcherthermal protection will be structurally capable of ensuring aircraftsurvival despite such an event.

Individual missiles are contained in canisters (FIGS. 4 a-5 d) thatserve as shipping containers and as launch tubes. The guide rail (FIGS.3 a-3 e) may be required to facilitate missile egress from the aircraft.The guide rail must be deployed rapidly into the air stream above theaircraft, must be capable of resisting air loads and dynamic loadsimparted by the missile as it exits, must release the missile withminimal tip-off, and must be retracted into the aircraft after launch,allowing launcher doors to close and seal the aircraft. It may bepossible to deploy and retract the rail using conventional motors in thetime required for the ABVL BMD mission, however, a self-erecting rail isproposed to ensure that the guide rail extension does not delay launch.Each canister incorporates the self-erecting launch rail as well asconnectors to the missile and front and aft closures that protect themissiles but allow egress upon launch.

The self-erecting launch rail slides in a cavity outside the forwardside of the canister (FIGS. 3 a-3 e) and this cavity fits inside acavity on the front side of each launch tube. These fixtures serve toindex the missiles on loading. Upon missile motor ignition, the rail ispulled upward by the missile during egress until it is stopped by amechanical limit that also unlatches the rail from the shoes attached tomissile structural frames at the top and bottom of the booster motor.The interceptor momentum and motor thrust then force the shoes along theremaining length of the rail until the motor exhaust nozzle clears theaircraft fuselage and launcher door tops. At this point, the shoes exitthe rail guides simultaneously at the top and bottom shoes (as is donein conventional naval guided missile rail launchers). The rail preventsthe lateral tipping moments (derived from airflow over the launcher)from causing excessive structural loads on the aft end of the missileand prevents a significant tip-off that would degrade missilecontrollability at egress. The rail is mechanically pulled back afteregress and the upper and lower doors are closed. Exhaust products fromthe rocket motor are purged by cross flow through the tube after missileexit as the launch rail is retracting and before the doors fully close.

After egress, the missile is controlled by a thrust vector control (TVC)or similar device attached to the missile booster. The missile autopilotachieves a flight path selected to assure stability while minimizingplume impingement on the aircraft until safe separation has beenachieved. In addition to normal operation considerations, the plannedmissile flight path is also selected such that possible missile failuremodes result in missile trajectories that are safe for the launchaircraft and aircrew. Egress safety is assured through the combinationof multiply redundant flight-critical equipment, automated pre-launchmissile functional operability testing, and physical design of themissile for stability and predictable flight path even should allcontrols fail subsequent to passing operability tests.

During flyout to the safe separation point, the aircraft establishesuplink and downlink communication with the missile. The links allowweapon control updates based on precision track of the ballistic missileto be sent to the missile, allow evaluation of missile health, and serveto improve the fire control solution based on actual (instead of nominala priori) missile performance. The missile is then commanded to anappropriate heading and flight path angle to best achieve interceptbased on the fire control solution passed to the missile uponinitialization. With vertical (or near vertical) launch, missilemaneuvers to a desired flight path angle will on average besignificantly smaller than for horizontal launch. Since all missilemaneuvers derive from propulsive energy, reducing these maneuversresults in higher missile burnout speeds and improved systemperformance.

In order to minimize structural modification to the aircraft and tominimize transient impacts on aircraft stability and control, it mayprove appropriate to achieve missile egress at lower thrust (and thuslower mass flow rate) than needed for the rest of boost. If this is thecase, egress would employ either a dual-thrust (low, then high) boosteror a small ejector motor capable of getting the missile to safeseparation conditions for full thrust. If “cold launch” is employed, themissile must be controlled using aerodynamic surfaces or with arocket-based attitude control system until booster motor ignition sinceTVC would not be available through the booster. The ignition of thebooster must then be achieved ensuring that no ignition debris isejected towards the aircraft. Further, the flight path of the missilemust assure that no collision with the aircraft can occur should thebooster fail to ignite.

The preferred seeker to be employed in ABVL BMD is a semi-active laserseeker. This seeker allows the weapon control system on the launchaircraft to designate the desired impact point on the target with alaser such that the ballistic missile payload is destroyed by directimpact at intercept (FIG. 1). The aircraft laser designator has opticalresolution adequate to ensure the designation of the threat payload atranges consistent with the defense missile intercept range. Preliminarycalculations indicate that the 1.5 m optics employed by the AirborneLaser (ABL) Ballistic Missile Defense System would be more than adequatefor intercepts at distances greater than 1000 km from the designatingaircraft. For the ABVL application, optics as small as 70 cm may beadequate. The laser designator spot size need not be smaller than about1 m at the target range since the seeker will aim at the centroid of theilluminated portion of the threat. Designation laser power andsemi-active laser (SAL) seeker sensitivity coupled with engagementgeometry, target geometry, and target materials will determine therequired spot size. Details of this analysis have not been done, but theABL designation laser and optical system would appear to have theperformance required to support the proposed ABVL BMD system.

Those skilled in the art will appreciate that the ABVL BMD method hasthe following unobvious advantages.

Air-Based Vertical Launch

ABVL results in surprising and unanticipated beneficial resultsregarding missile propulsion efficiency and hence missile size for agiven intercept condition. This is in addition to the expected benefitsof improved capacity and operational flexibility.

Background:

Air-based launch provides benefits of reduced atmospheric density andhence drag losses on missile performance. A horizontal launch, however,requires the aircraft to be generally aimed at the desired target orrequires the missile to use propulsive energy to redirect its trajectoryafter launch. If the aircraft must be turned to a new heading,significant delay (10's of seconds to minutes) is incurred which must bemade up through increased propulsion in the missile. If the missile isreleased on the wrong heading, a delay will be required (˜5 sec or more)before the commencement of a maneuver in order to allow for safeseparation from the aircraft to preclude potential collision. If themissile is released before motor ignition, further delays will beincurred. For a horizontal drop, this may add an additional 3-5 sec totime of flight. For parachute drop, this addition may be >5-10 sec. If aparticular intercept point is required (particularly the last effectiveintercept point), then each delay translates into a demand for a greateraverage velocity which also translates to greater burnout velocity. Fora given size payload, the increased demand in speed translates to abigger propulsion system. Since aircraft payload is usually limited,bigger missiles mean fewer missiles.

Vertical launch confers several advantages. First is an increase inmissile packing density and thus aircraft capacity. Second is theelimination of several delays in the launch sequence, which requiregreater propulsive energy. Third is the rapidity with which the missilereaches a desirable ascent altitude and the reduced time it takes to getto any given altitude. The reduced time to altitude means more of thepropulsive energy can go into acceleration of the mass rather thanfighting drag at lower altitudes. Even with a low-thrust egress,vertically-launched interceptors use the initial low-thrust phase toturn the missile to the proper flight path angle commensurate withmissile control (30-40 degrees) above the aircraft nose. The desiredflight path angle to the predicted intercept point is established afterbooster thrust ramp-up. Fourth is the ability to use the aircraft toprovide environmental protection for the missile prior to launch (ascompared to external launch configurations with comparable ignitiontimelines). For example, a 5-sec delay in launch sequence requires a 6%increase in velocity and a 12% increase in missile weight for aparticular intercept condition (range, altitude, and time available). A10-sec delay requires a 12% increase in velocity and a 35% increase inmissile weight.

Considerations:

Air basing has been considered for ballistic missile defense usinghorizontal launch including powered launch, drops, and parachuteextraction. All of these methods have serious consequences on engagementtimelines and missile propulsion. The size of the missile propulsion andinefficient horizontal orientations seriously limit missile-carryingcapacity for an individual aircraft. As a result, multiple aircraft mustbe airborne at a given defense point to provide capacity and coverage.All of these factors drive the total cost of a given level of defense.

Since surface ships employ vertical launchers for ballistic missiledefense, the use of a vertical launcher is not novel. Translation toaircraft may have been contemplated but several complications haveprevented serious consideration, in part because the unanticipatedbenefits were not understood, and in part because the consequences ofdelays have not been examined. Egress mechanisms that make verticallaunch from an aircraft practical make this solution novel.

It is important to note that a horizontal launch using parachutes toretard the missile and achieve vertical orientation before ignition hasbeen proposed. This is not vertical launch within the meaning of thisapplication.

First, most missions do not require the timeliness required for BMD.Alternately, missions (such as air-to-air intercept) that do requiresuch timeliness, generally have the aircraft oriented towards thetarget. This is not possible for most BMD scenarios because the launchlocation may not be known beforehand and because the aircraft mustperform some type of orbit to hold its desired position for long periodsof time. Under nominal conditions the threat launch will occur at arandom time in the orbit and the average offset angle is likely to be˜90°. Under the worst of conditions, an enemy may observe the aircraftorbit and fire when the offset angle is ˜180°.

In order to achieve vertical (or near-vertical) launch, there areseveral technical challenges to be met. First is protection of theaircraft structure against the transient effects of missile egress androcket exhaust. Second is the ability to protect the missile structureagainst tipping forces that occur upon egress at high aircraft speed.Third is the ability to control the missile's orientation after egressbut while the missile is flying at high aerodynamic angle of attack.Fourth is the ability to overcome safety concerns for ignition of arocket motor inside the aircraft.

Naval ships have had to solve all these problems in order to exploit theadvantages of vertical launch technology. There is a difference indegree however for the tip-off forces and for the missile stability andcontrol. The aircraft vertical launch system employs a self-erectingrail to aid egress, reduce loads due to tipping moments, and tofacilitate control authority in the missile during maximum angle ofattack. Alternate apparatus for egress control have also been inventedand presented herewith. The final preferred apparatus will be determinedthrough expensive tests not possible at this stage of invention.

Semi-Active Laser Seeker (SAL)

The SAL seeker employed in ABVL BMD results in surprising andunanticipated beneficial results regarding missile propulsion efficiencyand hence missile size for a given intercept condition. These benefitsare in addition to the intended benefits of lighter weight and lowercosts for laser seekers relative to infra-red (IR) seekers, lowercomplexity for guidance algorithms and thus software costs, and betterhit locations resulting in enhanced lethality without the need for akill enhancement device (KED).

Background:

SAL seekers exist in many smart weapon applications. Their use in BMDapplications has been considered, but the focus has been on IR seekersand radar seekers, both of which have high costs relative to SALseekers.

Because the ABVL platform can employ passive IR detectors and a laserranger for 3D track of the ballistic missile, the engagement timelinecan be compressed relative to other basing modes that depend on externalsensors to detect and track ballistic missile threats. Aircraft sensorsprovide the accuracy to point large-aperture optics at the boostingthreat, to resolve the threat at great range. These optics allow theaircraft to select the proper aimpoint and eliminate the need for themissile to make this determination at the last moment. Late aimpointselection is a significant risk for IR seeker guided missiles. If notachieved, the IR seeker will result in an adverse hit location from theperspective of payload destruction. If achieved, the kill vehicle muststill maneuver to move from the long-range aimpoint to the desired hitpoint. This can demand high thrust and impacts the KV mass and cost.

The SAL seeker has the proper aimpoint for the entire horning period,eliminating the late transients that create miss distance and drive theneed for a KED. Thus the SAL seeker reduces the mass and complexity ofthe KV by avoiding the coolant system weights demanded for IR seekers,reducing propellants needed for maneuvering, and by eliminating the needfor any KED and the propellants needed to maneuver the additional KEDmass. In addition, because the aircraft track of the ballistic missilepayload has “information inertia” that allows the correct object to betracked after burnout of the threat motor, intercepts can be achievedafter boost has ended even if countermeasures are deployed. This has theunintended consequence of significantly extending the availableengagement space with ABVL BMD relative to other guidance modes. Becausethe engagement window can extend past burnout, SAL guidance affordsascent phase intercept to the limits of the defense missile velocityadvantage. Because the efficiencies of vertical launch and SAL allow agiven missile to achieve a greater burnout velocity than for alternativeapproaches, more threats and circumstances can be covered.

Considerations:

Active lasers have been proposed for ballistic missile defense asdirected energy weapons, as fuse sensors, and as seekers.

In the case of laser seekers, the proposal has been made to employ alaser on the KV itself and to have the laser sensor then home on thetarget. This scheme is unlikely to be capable of directing the KV to thedesired aim point since doing so requires the KV guidance to beintelligent. In addition, it is unclear how the narrow laser beam canfind the target in the first place or be held on the target through KVmaneuvers, transient flight events, or in the presence ofcountermeasures.

In ABVL BMD operation, the air platform has the means of holding thedesignating laser on the correct portion of the target. The laser seekeron the KV need only be smart enough to find the laser spot and home toits centroid.

For the purpose of using a high-energy laser (HEL) to designate a targetto an IR seeker by heating the target to a specific temperature anduplinking the expected temperature to the defense missile, this schemeenables the intelligent ABL aircraft to employ its HEL in support ofsubsequent defense layers in the event that the threat ballistic missileis too far away for the HEL to be directly lethal or in the event that atarget cannot be engaged before end of boost due to firepower orcapacity of the HEL. This scheme represents an alternative defense modefor cooperative engagement between ABL and either ABVL or subsequentdefense layers, especially if intercepts by subsequent defenses willoccur after the threat complex evolves.

Air-Based Vertical Launch for Offensive Missiles

The ABVL system can also be employed for offensive missiles in the caseof time-critical strike missions as well as other offensive missions asillustrated in FIGS. 7 a and 7 b. For time-critical strike, the problemwith existing solutions is the delay between recognition of an emergenttarget and time-on-target for a weapon. Use of conventional weapons andlaunch platforms results in large numbers of platforms to distributeweapons around the battlefield such that at least one is in a favorableposition when a threat emerges. Employing a vertical launcher in awidebody aircraft and using ballistic missiles to provide extended rangecoverage with short flight times allows one or two aircraft to service alarge number of potential time-critical targets or to attack many lesstime-critical targets in coordinated fashion. An ABVL aircraft wouldcontain 32 or more strike missiles capable of impacting targets atranges of 500 miles or more from the aircraft at times less than 10minutes after target recognition, including delays for communications,engagement decisions, and missile initialization. The strike missiletime of flight would be minimal based on peak velocities as high as 7km/s depending on payload size. Assuming a 2000-lb class Joint DirectAttack Munition (JDAM) weapon as the payload, a 24-inch diameter boosterstack could achieve a 3-4 km/s burnout velocity with an overall missilelength of 20 feet including a protective shroud for the JDAM weapon. Theprotective shroud shields the JDAM from high temperatures duringacceleration and re-entry. The missile flight would be based on GlobalPositioning System (GPS) targeting. The missile would initialize theJDAM in the same manner as an aircraft so that release from theballistic missile would appear to the JDAM to be similar to release froman aircraft, albeit at potentially higher speed. The missile mightemploy a slowdown maneuver and deploy a retarding device to ensure JDAMrelease at close to conventional conditions depending on the costtradeoffs for hardening JDAM versus retarding the missile. Otherpayloads could include a laser-guided bomb for close air support and asubmunition payload for area targets. The ABVL aircraft couldpotentially serve both offensive time-critical strike and defensive BMDroles simultaneously given adequate capacity and a mixed missile load.The dual mission capability significantly improves the affordability andoperational flexibility of the ABVL platform. Aircraft stationing wouldlikely be driven by the need to conduct ballistic missile defense fromfavorable locations consistent with aircraft survivabilityconsiderations. Offensive missile reach would be adjusted throughmissile design to achieve the desired hostile country coverage from theTBMD stations. Additional console and land attack communications linkswould be incorporated into the ABVL BMC² system to provide for offensiveoperations. Referring to FIG. 7 a, a case is illustrated where noretardation would be required. In this case, aircraft deployed totheater based on 24 hr warning. Then 1-2 patrols are established using3-4 aircraft each. Theater assets detect time critical target, andcollect GPS location. Theater assets team pass time critical target IDand GPS location to ABVL TCS C2. Theater C2 selects target for actionand issues engagement order to TCS ABVL aircraft. Aircraft C2 receivesEO, assesses engageability and deconflicts airspace, responds withcomply/can't comply. Aircraft C2 Node accepts engage order therebyinitializing and launching the missile. The missile is initialized,launcher doors open, and dual thrust booster. The TVC provides safeegress, and ramps up to full thrust. The link antenna acquires andtracks missile beacon, establishes missile link, receives tactical TLM.Weapon control then updates, uplinks predicted intercept point. Boostusing bus GPS Guidance. In-flight updates are provided until burnout(command destruct capability until PGM separation). A slow-down maneuveris conducted if necessary to meet release conditions. There is then ahandover from bus GPS guidance to PGM GPS guidance with GPS update fromaircraft, followed by shroud separation, PGM payload release and PGMterminal flight using GPS guidance. Targeting assets can also providere-engagement decision data.

Referring to FIG. 7 b, a case is illustrated with retarded payloadrelease. Aircraft deploy to theater based on 24 hr warning then 1-2patrols are established using 3-4 aircraft each. Theater assets detecttime critical target and collect GPS location. Theater C2 selects targetfor action and issues engagement order to TCS ABVL aircraft. Aircraft C2receives EO, assesses engageability and deconflicts airspace, respondswith comply/can't comply. ABVLTCS C2 Node accepts engage order),initializes and launches missile, alerts force to trajectory. Themissile is initialized and launcher doors open and a dual thrust boosteris used and TVC provides safe egress, ramping up to full thrust. A linkantenna acquires and tracks missile beacon, establishes missile link andreceives tactical TLM. Weapon control then updates and uplinks predictedhand-over point. Boost is accomplished using bus GPS Guidance. In flightupdates are provided until burnout (command destruct capability untilSAL PGM separation). Ballistic flight (or aero-ballistic) is thenaccomplished, after which a slow-down maneuver is accomplished ifnecessary to meet release conditions. The booster then separates and thedrogue deploys. Handover from bus to SAL PGM guidance with final updateis accomplished after which the shroud separates and the droguereleased. The forward observer (or UAV) selects the aim point and useslaser designator to illuminate desired hit point. SAL PGM terminalflight using SAL guidance. The weapon impacts near laser spot withinlethal radius. The forward observer then provides mission assessmentdata, cue data for subsequent engagement.

Several methods/apparatuses for egress control may be used with themethod of this invention. These methods include hot plume diversion ofairflow (concentric or offset), cold plume diversion of airflow, egressrail-mounted airflow deflector, launcher-erected deflector,fuselage-mounted airflow deflector (including fairings), fixed-railsquare-tube canister, and inclined launcher (with or without rails)—allused in combination with dual-thrust booster, two-pulse booster, kickmotor, hot gas generator, cold gas generator, or airbag-type ejector toinitially clear the missile out of the aircraft.

A fixed tube array is the preferred embodiment of the launcher due toits simplicity relative to integration with the aircraft. However,mission flexibility may demand a modular launcher that can employ avariety of missile types and easily be reloaded to enable fastturn-around of an aircraft. FIG. 8 illustrates one such design. Amodular launcher may also allow incorporation of longer missiles (at theexpense of quantity) by leaning missiles forward in the individualmodules. Referring to FIGS. 8 a-8 f, Six rectangular modules instructural grid translates loads to aircraft structure. The exteriorgrid continues forward and aft of launcher section. The modules latch attop and bottom through open doors. Module doors hinge parallel toaircraft body centerline. Door opens over whole module as with a bombbay door. The top of each canister must withstand plume impingement fromadjacent rounds (fly-through cover). This arrangement simplifies upperand lower extensions by using'rectangular sections with structure toattach doors. Extensions are also coated with ablatives for thermalprotection. Launcher door actuators located in upper and lowerextensions.

FIG. 9 a illustrates an airflow deflector erected during launch by theaircraft. The deflectors are located in a cavity just upstream from eachmissile launch tube. An electric motor or hydraulic actuator erects thedeflector during the launch sequence. The deflector is retracted as soonas the missile clears the launch tube. The deflector shields the missilefrom the most severe egress loads until it can employ control tocompensate. The advantage of the launcher-erected deflector is that norail or gas diversion mechanisms are required. The disadvantage is theweight of the deflector and erecting mechanisms and the impact onpacking density due to the form factor of the deflector. Erection of thedeflector is expected to produce a transient (<2 sec) drag load of up to10,000 lbs on the aircraft.

Referring to FIG. 9 b, an alternate egress apparatus is shown wherein ahot plume diversion utilizes a portion of the booster gases to impart ahigh-velocity airflow upstream of the launch tube on the upper fuselage.This high-velocity flow diverts the free stream airflow around themissile body and greatly reduces the drag force and resulting pitchingmoment until the missile has cleared the top of the aircraft. At thispoint, the missile TVC can control the missile and compensate forcross-flow drag and pitching moment through the rest of the flight. Theplume is diverted by partially closing the aft end of the launch tube toincrease pressure within the canister. A portion of the gases isdiverted under this pressure through a tube (or tubes) on the front sideof the launch cylinder up to ports at the top of the fuselage.Supersonic nozzles designed for the expected range of operatingpressures accelerate the diverted gases to high velocity. Thehigh-velocity flow perpendicular to the aircraft velocity is “opaque” tothe airflow and causes it to divert around both the jet plume and themissile emerging just behind the jet plume. The flow will be complex andhas yet to be characterized in Computational Fluid Dynamics (CFD) codes.In principal, however, the high-velocity plume can shield much of themissile presented area from the ambient airflow and thus greatly reducethe egress transient loads and motions. The pressure in the launchcylinder will vary as the missile moves up the tube. As a result, theflow up the tube will eventually diminish. Significant design effortwill be required to optimize this approach. A variable diameter openingmay be required at the bottom of the launch tube to maintain adequatepressure to provide the desired plume velocity and height over theaircraft. In addition, the flow exhausted below the aircraft might needto use a nozzle to offset the thrust generated by the jets at the top ofthe fuselage. While FIG. 9 b illustrates one tube with severalsupersonic nozzles, the actual preferred arrangement may include onetwo-dimensional nozzle covering the front of a cell and may not requirean actual nozzle depending on the flow velocity and its ability todeflect the airflow.

Referring to FIG. 9 c, a related apparatus would use a concentric tubeoutside the canister to divert a portion of the exhaust gases back tothe top of the aircraft. A convergent-divergent annular nozzle would beused at the top of the cylinder to provide a sheaf of high-velocitygases around the missile as it emerges. A convergent-divergent nozzlewould be used at the bottom of the cylinder to provide compensatingthrust at the bottom of the aircraft and to keep the concentric tubeadequately pressurized. The illustration employs several conventionalnozzles rather than a single annular one. The actual nozzleconfiguration will be resolved with FCD analysis and optimization offlow.

FIG. 9 d illustrates a cold (or warm) gas system for achieving thedesired airflow deflection. Here a single source is used to generate thedesired gas pressure. A manifold system is used to flow the gas to thedesired launch tube. Complexity of the manifold system is expected to bethe principal issue with this approach. The principal advantage is thatit does not require additional motors or significant diversion boosterexhaust products. Again, no rail is required. Also the same discussionof nozzle configuration applies: the actual optimal configuration willbe derived through CFD analysis.

In order to provide a steady diversion flow, it may be desirable toinstall hot gas or even cold gas generators ahead of each launch tube.FIG. 9 e illustrates the use of several small solid rocket motorsupstream of the launch tube to achieve this goal. These motors would beignited during the launch sequence at the time appropriate to minimizethe egress loads on the missile. Burn times would be ˜1 sec, beginning˜0.25 sec after booster ignition. A low-cost motor such as the 70 mmHydra rocket motor could provide this divert flow. The motors would fiton the forward side of the launch canister and be loaded with the all-upround into the aircraft. The thrust generated by the small motors isexpected to be small enough that compensation will not be necessary fora large aircraft. Again, CFD analysis will be required to tune thisdesign for alternative missiles, but the advantage is that no rail wouldbe required.

FIG. 9 f illustrates a hybrid approach of the launcher-erected airflowdeflector (from FIG. 6 a) topped with a high-velocity plume to shieldthe whole missile. In this case, the airflow deflector coversapproximately half of the exposed missile. The motors are installedinside the fairing at its top. The motors are fired as the missileemerges, shielding the top of the missile until it has cleared theaircraft.

FIG. 9 g illustrates a fixed launch rail in a square canister. Thiscanister may be vertical or it may lean forward in the aircraft. Slotson the leading side of the canister keep the missile from pitching backuntil the front shoes leave the slot. The missile accelerates quicklysuch that the aft shoes exit ˜0.25 sec after the front shoes. Thepitching moment on the missile through this time generates only a smallangular change for the missile body (1-2 deg) even though the rate maybe significant (20-25 deg/sec). Since there is clearance between themissile and the aft side of the canister, the missile tail section doesnot need to be structurally capable of dealing with a 100,000 ft-lbbending moment. In the case of a forward-leaning launcher, the leanangle can be used to partially compensate for the initial tip-offmotions. The added advantage of a square canister is that aerodynamicsurfaces can be accommodated without folding. This simplifies egress formissiles needing aerodynamic surfaces for stability and/or control. Thepotential disadvantage of square launchers includes form factor andpacking density issues and difficulty of incorporating gas diversiontechniques discussed above.

FIGS. 10 a-10 d illustrate hot and cold launch alternatives consideredappropriate for ABVL. The preferred method is hot launch by a dualthrust motor for large missiles and a full thrust motor for smallermissiles. It is expected that motor thrust of 20,000 lbs or less willrequire modest protection for the aircraft structure. Significantlylarger motors will likely require significant protection increases or alow-then-high thrust profile as previously described. A motor that burnsfor ˜1 sec and then shuts down may get the missile out of the aircraftwith sufficient velocity to allow flight to a desired safe separationfor re-ignition. While still in the canister, thrust can besignificantly higher than 20,000 lbs. For a motor with 40,000 lbs thrustand a missile weighing 8,000 lbs, the motor would burn for 0.56 sec (toburn out before the nozzle exits the aircraft) and the missile woulddepart the airplane at 72 ft/sec. While this velocity would allow themissile to clear the tail, it's too low to preclude fallback before safeseparation; apogee would be 80 ft (40 ft above the tail). In general,higher thrust (˜100,000 lbs) would be needed and for shorter durations(0.33 sec) to yield ˜200 ft of clearance before booster ignition.Inclined launchers or fairings that extend acceleration distance makeshort-pulse motors somewhat more attractive (+5 ft of travel adds 20 ftof clearance in the vertical case above). Short durations make 2-pulseor ejector motor rocket propulsion less desirable (and less achievable)and forces consideration of other techniques such as airbag ejection,hot gas ejection, cold gas ejection, or gun launch.

A desirable safe separation is ˜200 ft above the aircraft with positiveupward velocity and stable orientation. This condition requires egressat ˜120 ft/sec if there is no propulsion after egress. Achieving thisvelocity requires about 9 g's of acceleration through the 20 ft launchtube. It also requires aerodynamic stability and control or otherattitude control systems during the coast to booster ignition. Gunlaunches provide 100's of gees of acceleration but are incompatible withthe large missiles here considered due to structure and instrumentsurvivability. Average pressure in the tube for cold or warm gas launchor for airbag launch must be 18,000 lbs/ft², a difficult value for atube volume of ˜111 cu ft. In addition, these egress alternativesrequire the aircraft to absorb the needed momentum transfer (˜975,000ft-lb/sec). Thus, a dual-thrust launch appears to be the preferredegress technique for air-based vertical launch of large missiles.

Referring to FIG. 10 a, a missile 140 is shown being launched from theaircraft 10. There would be local blast and thermal protection 142 onthe aircraft and straight through recoil-less exhaust 144. Either a hotlaunch or a cold launch could be employed. A small ejector motor couldalso be used.

Referring to FIG. 10 b, a hot launch missile 146 is shown. With thismissile there would be full ignition inside the aircraft so thatsuitable structural protection would be required as for example, byproviding increased structure in the launcher area to resist blast,shock and mass flow impingement. Suitable thermal additives, points,tiles and high temperature allows may also be used. The dual thrustbooster provides a low initial burn rate which reduces blast shockthermal and erosion loads.

Referring to FIG. 10 c, a missile 148 is shown. this missile is equippedwith a dual thrust booster provides a slow burn rate.

Referring to FIG. 10 d, a missile 150 with a small ejector motor 152 maybe used. Such a missile, achieves safe separation before main motorignition, reduces protection needs, and reduces transients. It will beappreciated that this embodiment requires attitude control during coastand requires a safe post separation trajectory.

Referring to FIG. 10 e a cold launch missile 154 with an analog 156 orgas container may be used. This missile requires a delayed igniter,attitude control during coast, and structural stiffening to absorbmomentum transfer. The embodiment would minimize transient aerodynamics.

FIGS. 11 b-11 c illustrate forward-leaning launchers from vertical to˜45 degrees forward of vertical (all considered vertical or“near-vertical” in this invention context) as compared to the verticalarrangement shown in FIG. 11 a. Forward lean reduces egress loads on themissile by reducing angle of attack and presented area. However, forwardlean increases the size of the launcher and or reduces the number ofmissiles that can be carried in an upward firing launcher. In addition,leaning the launcher makes insertion of missiles much more complex.Initial analyses of the benefits of launcher lean do not revealsignificant value compared to the preferred method of vertical launch.However, a near vertical launcher with ˜15-20 degrees lean may stillobtain the other benefits of vertical launch such as rapid selection ofmission-specific missiles, rapid recovery from a missile fault atinitialization, and perhaps only modest loss of space in the aircraftand modest increase in the difficulty of loading the aircraft. Whethercost savings from the reduction in egress loads compensates for the costimpacts of these minor degradations is still to be determined.

FIGS. 12 a-12 c illustrates several configurations for fixed airflowdeflecting fairings. These have the disadvantage of producing dragthroughout flight but have the advantage of always being present.Effectiveness of fixed fairings and deflectors for reducingairflow-induced loads and transient motion on ABVL missiles is notexpected to warrant their cost in aircraft performance. Long enduranceof the aircraft is a significant factor in providing defense or offensewhere the target emerges at unknown times over long periods ofdeployment (months).

While the present invention has been described in connection with thepreferred embodiments of the various figures, it is to be understoodthat other similar embodiments may be used or modifications andadditions may be made to the described embodiment for performing thesame function of the present invention without deviating therefrom.Therefore, the present invention should not be limited to any singleembodiment, but rather construed in breadth and scope in accordance withthe recitation of the appended claims.

1. A method for providing a defense against a ballistic missilecomprising the steps of: mounting an intercepting missile in anapproximately vertical position in an aircraft; then acquiring andtracking the ballistic missile; and then launching the verticallymounted missile and impacting the ballistic missile with saidintercepting missile.
 2. The method of claim 1 wherein the missile isvertically mounted.
 3. The method of claim 1 wherein the missile ismounted in a tilted position.
 4. A method for launching an offenseballistic missile comprising the steps of: mounting a ballistic missilein an approximately vertical position in an aircraft; then recognizingan emerging target (or accepting an order to fire given in GPScoordinates); and then launching the ballistic missile, whereby atime-critical strike can be accomplished with a reduced number oflaunching platforms.
 5. The method of claim 3 wherein the missile isvertically mounted.
 6. The method of claim 3 wherein the missile ismounted in a tilted position.
 7. A method for launching a satellite intoearth orbit comprising the steps of: mounting a launch vehicle in anapproximately vertical position in an aircraft; flying the aircraft to aposition to place the satellite in the preferred orbit; and thenlaunching the satellite launch vehicle, whereby an economicallyadvantageous small satellite can be accomplished or whereby a set ofsatellites may be launched into a series of related orbits within ashort time with a reduced number of launching platforms.
 8. The methodof claim 6 wherein the launch vehicle is vertically mounted.
 9. Themethod of claim 6 wherein the launch vehicle is mounted in a tiltedposition.
 10. A method for launching naval mines into a minefield fromgreat standoff comprising the steps of: placing the mine in a missilebus consisting of a dual-thrust booster with thrust vector control(TVC), a global positioning system (GPS)-aided inertial navigationsystem (INS), a retarding device, a separating shroud, and a mineinitialization and safety arming device; mounting the missile bus in anapproximately vertical position in an aircraft; launching a set of minebuses to release their mines into a prescribed grid location based onGPS coordinates, whereby minefield can be safely deployed to a desiredlocation without exposing a number of launch platforms to heavy airdefenses.
 11. The method of claim 9 wherein the missile bus isvertically mounted.
 12. The method of claim 9 wherein the missile bus ismounted in a tilted position
 13. A method for launching UAVs from greatstandoff comprising the steps of: placing the UAV in a missile busconsisting of a dual-thrust booster with TVC, a GPS-aided INS, aretarding device, a separating shroud, and a UAV initialization device,mounting the missile bus in an approximately vertical position in anaircraft, launching the UAV bus to release the UAV at a prescribedlocation based on GPS coordinates.
 14. The method of claim 12 whereinthe missile bus is vertically mounted.
 15. The method of claim 12wherein the missile bus is mounted in a tilted position
 16. A method forlaunching a missile having a motor from a launch tube comprising thesteps of: positioning a self-erecting launch rail slide in the cavity onone side of the launch tube so as to index the missile on loading;igniting the missile motor so that the rail is pulled upwardly by themissile during egress from the launch tube until the rail is stopped bya mechanical limit that also unlatches the rail from shoes attached tothe missile and forcing the shoes along the remaining length of the railuntil the motor clears the aircraft, whereby lateral tipping motions areprevented.
 17. A method for launching a missile having a motor from alaunch tube comprising the steps of: positioning rocket nozzles upwindof each launch tube; expelling high-velocity gases from a rocket motor,the missile motor, or some other gas generator through the nozzlesadjacent to the launch tube; deflecting the ambient airflow around themissile using the gas flow so created until the missile has egressedfrom the launch tube; reducing thereby the drag loads on the missile andthe resultant tipping forces.
 18. A method for launching a missilehaving a motor from a launch tube comprising the steps of: positioningan erectable deflector upwind of each launch tube; extending thedeflector during the launch sequence using motors or hydraulicactuators; deflecting the ambient airflow around the missile using thedeflector until the missile has egressed from the launch tube; extendingthe height protected through the use of high-velocity gas jets mountedin the top of the deflector; withdrawing the deflector back into thelauncher; reducing thereby the drag loads on the missile and theresultant tipping forces.